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A sample wind tunnel layout showing some typical features including a test section and control room, a machine for pumping air continuously through ducting, and a nozzle for setting the test airspeed. A wind tunnel is "an apparatus for producing a controlled stream of air for conducting aerodynamic experiments". [1]
An atmospheric layer wind tunnel and multiple flumes were also added to the collection of research facilities. This was made possible through funding from the National Science Foundation (NSF). From 1977 through 1993, the Laboratory emphasized the integration of education and basic and applied research.
The University of Tennessee Space Institute (UTSI) is a satellite campus of the University of Tennessee located near Tullahoma, Tennessee.. UTSI was founded to allow students to take advantage of the aerospace facilities located in the Arnold Engineering Development Center on Arnold Air Force Base, including wind tunnels and other laboratory equipment.
The National Wind Institute (NWI) at Texas Tech University (TTU) was established in December 2012, and is intended to serve as Texas Tech University's intellectual hub for interdisciplinary and transdisciplinary research, commercialization and education related to wind science, wind energy, wind engineering and wind hazard mitigation and serves faculty affiliates, students, and external partners.
Low Speed Wind Tunnel 1.15 m (3 ft 9 in) by 0.95 m (3 ft 1 in) Flow Visualisation Wind Tunnel 0.90 m (2 ft 11 in) by 0.90 m (2 ft 11 in) United Kingdom University of Manchester [17] Operational Hypersonic wind tunnel 6 in (150 mm) diameter Trisonic wind tunnel 0.15 m (5.9 in) by 0.3 m (1 ft 0 in)
The low-speed wind tunnel is a closed-circuit, continuous flow tunnel with a 100 hp, variable frequency drive. The test section measures 0.6 by 0.9 meters and is capable of flow velocities up to 50 m/s. It is equipped with 3 and 6 component force balances and a PC-based multiplexed data acquisition system. Smoke visualization is also available.
The facility was designed to provide ground-based simulations of supersonic and hypersonic flight conditions. The combustion air heater can provide total pressures from 200 psia to 2,800 psia (13.6 atm to 190.5 atm) and a total temperatures from 1,200°R to 4,700°R (667 K to 2,611 K).
In 1934 the world's largest wind tunnel was constructed at Langley Field with a 30-by-60-foot (9.1 m × 18.3 m) test section; it was large enough to test full-scale aircraft. [ 9 ] [ 10 ] It remained the world's largest wind tunnel until the 1940s, when a 40-by-80-foot (12 m × 24 m) tunnel was built at NASA's Ames Research Center in California.